One example aspect of the present disclosure is directed to a method for implementing modularized logic. The method includes accessing, by one or more processors, control software implemented on a controller to control operation of an aircraft engine. The method includes accessing, by the one or more processors, at least one of a plurality of propeller configuration parameters. The method includes modifying, by the one or more processors, the accessed at least one of the propeller configuration parameters independently of the control software.

There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.

There are described methods and systems for providing an autothrottle mode in a propeller-driven aircraft. A thrust change is obtained corresponding to a difference between an actual thrust and a desired thrust for an engine. When greater than a pre-determined threshold, a setting change to one or more control input(s) of the engine is determined. One or more commands is output to cause the setting change of the control input(s).

A propulsion system for a hybrid electric vehicle comprises a traction motor having first and second stator windings; a power source having a DC power output coupled to the first windings; a battery having a DC power output coupled to the second windings; and a controller to independently control: (i) a first power level output at the first DC power output, and (ii) a second power level of motive power output by the traction motor; wherein responsive to a signal to set the second power level less than full capacity of the traction motor, the controller provides a power difference between the first and second power levels from the second windings to the battery.

Propeller control systems and methods for controlling the pitch of a plurality of propeller blades of a variable pitch propeller assembly operatively coupled with an engine is provided. In one exemplary aspect, the propeller control system includes features for combining overspeed and feathering protective functions in a protective control valve communicatively coupled with a controller. In such an event the controller controls the protective control valve to selectively allow a controlled amount of hydraulic fluid to flow to or from a pitch actuation assembly such that the pitch of the propeller blades can be adjusted based at least in part on the condition of the engine.

A propeller for an aircraft turbomachine, the propeller having; a hub extending around a first axis including openings distributed around the first axis, each of the openings having a substantially radial orientation relative to the first axis and extending through the hub, a system for controlling the angular setting of a blade which is mounted in each of the openings, and bearings for guiding the control system, which are mounted in each of the openings, the guide bearings including two guide bearings, one of which includes two annular rows of angular contact coaxial balls having different diameters.

A turboprop control system 10 for use with a turboprop 2 having a turbine engine 12 operably coupled to and rotationally driving a propeller 14 having variable pitch blades 16 to control the engine speed, propeller speed, and propeller pitch. The pilot provides, by a single power control lever 30, the control input used to control the engine and propeller.

The invention relates to a means (27) for controlling a system for changing the pitch of blades of a turbine engine propeller, the control means (27) comprising a fixed member (28) and a member (29) which is movable in translation along a longitudinal axis (X) relative to the fixed member (28), and an anti-rotation device (33) configured so as to prevent the rotation of the movable member (29) relative to the fixed member (28) about the axis (X).

According to the invention, the anti-rotation device comprises a longitudinal structural crossmember (35) which is mounted by means of a first and a second end (36, 37) on the fixed member, and support and guide means (57) integrally in translation the movable member along the axis (X), the crossmember extending radially outside the movable member and the fixed member relative to a radial axis (Y) which is perpendicular to the axis (X) and being guided through the support and guide means.

A single input engine controller and system are provided for translating a single input indicative of the amount of fuel to be supplied to an engine from a fuel control interface into separate signals for controlling the amount of fuel supplied to the engine and the RPM of a propeller powered by that engine. The single input controller translating the single input into the separate signal for the RPM of the propeller according to a fuel efficiency relationship between the fuel amount and the propeller RPM.

There is described herein methods and system for correcting steady state errors in propeller speed by calculating a leakage flow rate as a function of engine and propeller parameters.